Impact disintegration test fragment recovery device

Abstract

The invention relates to the technical field of space debris capture, in particular to an impact disintegration test debris recovery device which comprises a target chamber and a capture structure, a target cavity is formed in the target chamber, and the target cavity is used for containing a simulation target; the capturing structure is arranged on the inner wall of the target cavity and comprises a first capturing layer and a second capturing layer, the second capturing layer covers the inner wall of the target cavity, the first capturing layer covers the face, away from the inner wall of the target cavity, of the second capturing layer, the density of the first capturing layer is smaller than that of the second capturing layer, and the first capturing layer is of a transparent structure. Small-size and small-kinetic-energy tiny fragments are captured by the first capturing layer, large-size and large-kinetic-energy fragments penetrate through the first capturing layer to be captured by the second capturing layer, the number of the tiny fragments entering the second capturing layer is reduced, and therefore positioning and extraction of the large fragments in the second capturing layer based on X-rays and a section method are facilitated. And the first capturing layer is of a transparent structure, so that the difficulty of extracting the tiny fragments is reduced.

Description

Technical Field

[0001] The present application relates to the technical field of space debris capture, and in particular to a debris recovery device for impact disintegration tests. Background Art

[0002] The purpose of the space debris impact disintegration test is to obtain the disintegration threshold, characteristic size, surface-to-mass ratio and quantity distribution of disintegrated fragments, and provide technical support for the establishment and improvement of the space debris environment model. The impact velocity in the disintegration test usually belongs to the range of hypervelocity impact. Modern typical satellites have complex structures and many types of materials. Under strong impact, the fracture and failure of materials and structures are irregular. The characteristics of the disintegration fragments of spacecraft models are extremely complex. Not only are the numbers huge, but the materials of the disintegration fragments are of many types, the shapes are complex, and the scale spans a large range, which brings great challenges to the recovery and extraction of the disintegration fragments.

[0003] At present, the soft recovery method of foam board is mainly adopted in the impact disintegration test. The specific method is to stick the foam layer on the plywood of the inner wall of the target chamber. The foam layer adopts two or three density designs to capture fragments of different speeds. After the test, X-ray scanning is used to give the spatial distribution of fragments in the foam board.

[0004] First of all, this method mainly solves the problem of recycling fragments larger than 2mm. The recycling of fragments below 2mm is too difficult and is basically not considered. Secondly, after the method recovers the fragments, X-ray scanning is used to accurately locate the disintegrated fragments in the foam board. Due to the characteristics of X-rays themselves, there are certain defects in the scanning process. On the one hand, the information of some fragments that are transmissive to X-rays will be lost, resulting in some fragments that cannot be captured by scanning, causing quality loss of the recycled disintegrated fragments. On the other hand, a large number of tiny-sized fragments are embedded in the foam board, and X-ray scanning, positioning and extraction are very time-consuming and laborious. If the foam board splitting method is used, it will also lead to the problem that the recovery of fragments takes too much time and the tiny fragments are difficult to find. Therefore, the method of recycling foam boards has deficiencies and difficulties in extracting tiny fragments, and this method is basically unable to recycle small fragments below 2mm. Summary of the invention

[0005] The present application provides a fragment recovery device for an impact disintegration test, which is used to solve the problem in the prior art that tiny fragments generated by an impact disintegration test are difficult to extract and have a low recovery rate.

[0006] The present application provides a fragment recovery device for impact disintegration test, comprising: A target chamber, wherein a target cavity is formed inside, and the target cavity is used to place a simulated target; The capture structure is arranged on the inner wall of the target cavity, and the capture structure includes a first capture layer and a second capture layer. The second capture layer covers the inner wall of the target cavity, and the first capture layer covers the side of the second capture layer away from the inner wall of the target cavity. The density of the first capture layer is less than that of the second capture layer, and the first capture layer is a transparent structure.

[0007] In one possible design, the first capture layer is a multi-layer membrane structure.

[0008] In a possible design, the first capture layer includes a flexible film, the flexible film has at least two layers, and an inclusion portion is formed between two adjacent layers of the flexible film.

[0009] In a possible design, bubbles are uniformly formed between two adjacent flexible films through intermittent bonding.

[0010] In one possible design, the bubbles are circular.

[0011] In a possible design, the distance between two adjacent bubbles is smaller than the diameter of the bubbles.

[0012] In one possible design, the diameter of the bubble is 6 mm-25 mm; and / or the thickness of the bubble is 2 mm-12 mm.

[0013] In one possible design, the density of the flexible membrane is 0.015 g / cm 3 -0.045g / cm 3 .

[0014] In one possible design, the density of the second capture layer is 2-4 times the density of the flexible membrane.

[0015] In one possible design, the second capture layer is a foam board structure.

[0016] The beneficial effects of this application are as follows: The fragment recovery device for impact disintegration test of the present application is provided with a first capture layer and a second capture layer on the inner wall of the target chamber, wherein the first capture layer is close to the simulated target. After the projectile hits the simulated target, the simulated target disintegrates under the action of the impact force to produce fragments of different sizes, and the fragments rush to the surrounding first capture layer and second capture layer. Since the density of the first capture layer is less than that of the second capture layer, on the one hand, tiny fragments with smaller size and smaller kinetic energy are directly captured by the first capture layer. Since the first capture layer is a transparent structure, it is convenient to directly locate and extract the tiny fragments inside it, thereby improving the recovery rate of the tiny fragments. On the other hand, fragments with larger size and larger kinetic energy pass through the first capture layer and enter the second capture layer and are captured by the second capture layer. Since the tiny fragments are basically intercepted by the first capture layer, the number of tiny fragments entering the second capture layer is effectively reduced, thereby facilitating the positioning and extraction of larger fragments in the second capture layer based on X-rays and the profile method, greatly improving the recovery rate of the fragments, and more significantly reducing the difficulty of fragment extraction, thereby improving the efficiency of fragment extraction. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the specific implementation methods of the present application or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0018] Figure 1 A schematic diagram of the structure of a fragment recovery device for impact disintegration test provided in an embodiment of the present application; Figure 2 A schematic diagram of the structure of the first capture layer of the impact disintegration test fragment recovery device provided in an embodiment of the present application.

[0019] Reference numerals: 100, target chamber; 110, target cavity; 200, simulated target; 310, first capture layer; 311, flexible membrane; 312, air bubble; 320, second capture layer. DETAILED DESCRIPTION

[0020] The technical solution of the present application will be described clearly and completely below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without creative work are within the scope of protection of the present application.

[0021] Combine the following Figure 1-Figure 2 , describing the impact disintegration test fragment recovery device provided in the embodiments of the present application.

[0022] Reference Figure 1 As shown, the fragment recovery device for the impact disintegration test provided in the embodiment of the present application includes a target chamber 100 and a capture structure. A target cavity 110 is formed inside the target chamber 100, and a vacuum environment is simulated in the target cavity 110, which is used to place a simulated target 200 during the test. For example, the simulated target 200 is a spacecraft model, and the spacecraft model is placed in the middle of the target cavity 110. By firing a projectile at the spacecraft model, the spacecraft model is disintegrated under the impact force of the projectile, and the fragments of the disintegrated spacecraft model will rush to the inner wall of the target chamber 100. After the test, it is necessary to recover all the fragments of the spacecraft model as much as possible, and by obtaining the disintegration threshold, the characteristic size of the disintegrated fragments, the surface-to-mass ratio, and the number of distributions, technical support data is provided for the establishment and improvement of the space debris environment model. Among them, the capture structure is a structure used to capture the fragments of these spacecraft models.

[0023] The capture structure covers the inner wall of the target cavity 110 except the test window. Specifically, the capture structure includes a first capture layer 310 and a second capture layer 320, and avoidance windows for avoiding the test window are respectively opened on the first capture layer 310 and the second capture layer 320. The second capture layer 320 covers the inner wall of the target cavity 110 and is in direct contact with the inner wall of the target cavity 110. The first capture layer 310 covers the side of the second capture layer 320 away from the inner wall of the target cavity 110, that is, the side close to the simulated target 200. The disintegrated fragments first reach the first capture layer 310 and then reach the second capture layer 320. Among them, the density of the first capture layer 310 is less than the density of the second capture layer 320, and the first capture layer 310 is a transparent structure, for example, the first capture layer 310 is a transparent film layer. In this way, tiny fragments with smaller size and smaller kinetic energy are directly captured by the first capture layer 310. Since the first capture layer 310 is a transparent structure, it is convenient to observe the position of the tiny fragments inside it, reducing the difficulty of locating and extracting the tiny fragments, and improving the recovery rate of the tiny fragments; fragments with larger size and greater kinetic energy are sufficient to pass through the first capture layer 310 and enter the second capture layer 320 and be captured by the second capture layer 320. Since the tiny fragments are basically intercepted by the first capture layer 310, the number of tiny fragments entering the second capture layer 320 is effectively reduced, thereby facilitating the positioning and extraction of larger fragments in the second capture layer 320 based on X-rays and profiling methods, thereby improving the overall recovery rate of the fragments, reducing the difficulty of fragment extraction, and improving the extraction efficiency of the fragments.

[0024] In some specific embodiments provided in the present application, the first capture layer 310 is a multi-layer film structure, and the number of film layers is set according to the test parameters of the projectile and the simulated target 200, for example, the number of film layers can be two layers, three layers, four layers, etc. By designing the first capture layer 310 as a multi-layer film, each layer of the film is a transparent film, and the multi-layer film structure retains the transparent characteristics of the film while also having a certain impact resistance, so that small fragments with small volume and small kinetic energy are intercepted, and large fragments with large volume and large kinetic energy penetrate and smoothly reach the second capture layer 320. And because the film is soft in texture, the multi-layer film can hold the intercepted tiny fragments on the multi-layer film, which is convenient for extraction and recovery.

[0025] In some specific embodiments provided in the present application, the first capture layer 310 includes a flexible film 311, and the flexible film 311 is at least two layers, for example, the flexible film 311 is two layers, three layers, four layers, etc. Specifically, the flexible film 311 is a transparent polyethylene film, which is light in weight, has good transparency, and has excellent impact absorption performance. The number of layers and thickness of the flexible film 311 can be determined according to the impact parameters of the impact test and the spacecraft model parameters, for example, according to the diameter and speed of the projectile and the original mass of the projectile and the spacecraft, so that the first capture layer 310 can capture as many tiny fragments of millimeter level and below as possible. An inclusion portion is formed between two adjacent layers of flexible film 311, and the porosity of the inclusion portion is relatively large. For example, the inclusion portion is a hollow structure formed between two adjacent layers of flexible film 311, and the hollow structure is used to provide a certain gap between the two adjacent layers of flexible film to accommodate the fragments intercepted by the flexible film 311, and also facilitate the fragments to detach from the hollow structure.

[0026] Reference Figure 2As shown, in some specific embodiments provided in the present application, the containing portion can also be a bubble 312. Specifically, a plurality of bubbles 312 are evenly formed between two adjacent layers of flexible film 311 by intermittent bonding. The shape of the bubble 312 can be circular, rectangular, irregular, etc. Preferably, the shape of the bubble 312 is circular, and the circular bubble 312 can avoid the appearance of sharp corners around the bubble 312, which is conducive to maintaining a certain impact resistance of the flexible film 311 and intercepting debris. At the same time, when the area of ​​the flexible film is constant, the number of circular bubbles 312 will be greater, which is conducive to increasing the effective capture area of ​​the flexible film 311. In this way, by bonding two adjacent layers of flexible membrane 311 in an intermittent manner to form a plurality of bubbles 312, firstly, the distance between the two adjacent layers of flexible membrane 311 can be increased without adding other materials, so that the fragments penetrating or embedded in the previous layer of flexible membrane 311 can be temporarily stored in the corresponding bubbles 312; secondly, there is only air in the bubbles 312, and the bubbles 312 will not cause secondary damage to the fragments, and the original shape of the fragments can be restored more realistically; thirdly, the bubbles 312 are hollow, so that the first capture layer 310 as a whole maintains a high degree of transparency, which makes it easy to observe the position of the fragments embedded in the flexible membrane 311 or in the bubbles 312 when recovering the fragments, so as to facilitate extraction.

[0027] In some specific embodiments, the distance between two adjacent bubbles 312 is smaller than the diameter of the bubble 312. In this way, the effective capture area of ​​the entire flexible film 311 can be increased as much as possible. Specifically, the diameter of the bubble 312 is 6 mm-25 mm, for example, the diameter of the bubble 312 is 6 mm, 10 mm, 15 mm, 50 mm, 25 mm, etc. The thickness of the bubble 312 is 2 mm-12 mm, for example, the thickness of the bubble 312 is 2 mm, 4 mm, 6 mm, 8 mm, 10 mm, 12 mm, etc. The density of the flexible film 311 is 0.015 g / cm 3 -0.045g / cm 3 For example, the density of the flexible film 311 is 0.015 g / cm 3 , 0.025g / cm 3 , 0.035g / cm 3 , 0.045g / cm 3 wait.

[0028] In some specific embodiments provided in the present application, the second capture layer 320 is a foam board structure. The density of the second capture layer 320 is 2-4 times the density of the flexible film 311. For example, the density of the second capture layer 320 is 0.135 g / cm 3 In this way, it is possible to prevent fragments with large volume and large kinetic energy from passing through the second capture layer 320 and thus avoid damaging the target chamber 100 .

[0029] Before conducting the experiment, the density and number of layers of the flexible film 311, the thickness and diameter of the bubbles 312, and the density and thickness of the second capture layer 320 must first be determined. The specific design method is as follows: According to the impact parameters of the experimental design and the spacecraft model parameters, the impact kinetic energy and the mass ratio of the impacted object EMR are calculated, where EMR=E / M, E is the impact kinetic energy, M is the mass of the impacted object M, and the impacted object is the spacecraft model; According to the calculated EMR, the impact disintegration situation is preliminarily judged, and the density and number of layers of the flexible film 311 and the diameter and thickness of the bubble 312 are designed; the density and thickness of the second capture layer 320 are designed; Laying a second capture layer 320 on the inner wall of the target chamber 100, so that the second capture layer 320 covers other positions of the inner wall of the target chamber 100 except the test window; Laying the first capture layer 310 on the second capture layer 320, the first capture layer 310 covers other positions of the second capture layer 320 except the test window; Install spacecraft models, debug test equipment, and start experiments; After the experiment, the first capture layer 310 and the second capture layer 320 are recovered respectively; wherein the debris on the first capture layer 310 can be directly observed and extracted, and the second capture layer 320 can be extracted by using the cross-section method after locating the debris by X-ray scanning; Measure the mass of the extracted disintegration fragments respectively, obtain the total mass of the recovered disintegration fragments, and calculate the mass ratio of the recovered fragments N%, where N%=M d / (M p +M s ), M d is the total mass of the recovered debris, M p is the mass of the projectile, M s is the mass of the simulated target 200; The recycling effect is evaluated based on the mass ratio of the recovered fragments; The density and number of layers of the flexible film 311 , the diameter and thickness of the bubbles 312 , and the density and thickness of the second capture layer 320 are adjusted according to the recovery effect.

[0030] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0031] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of this application, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0032] In this application, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0033] In the present application, the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0034] Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and cannot be understood as limitations on the present application. Ordinary technicians in this field can change, modify, replace and modify the above embodiments within the scope of the present application.

Claims

1. A fragment recovery device for impact disintegration test, characterized in that: include: A target chamber, wherein a target cavity is formed inside, and the target cavity is used to place a simulated target; A capture structure is arranged on the inner wall of the target cavity, and the capture structure includes a first capture layer and a second capture layer, the second capture layer covers the inner wall of the target cavity, the first capture layer covers a side of the second capture layer away from the inner wall of the target cavity, the density of the first capture layer is less than the density of the second capture layer, and the first capture layer is a transparent structure.

2. The fragment recovery device for impact disintegration test according to claim 1, characterized in that: The first capture layer is a multi-layer film structure.

3. The fragment recovery device for impact disintegration test according to claim 2, characterized in that: The first capture layer includes a flexible film, the flexible film has at least two layers, and an inclusion portion is formed between two adjacent layers of the flexible film.

4. The fragment recovery device for impact disintegration test according to claim 3, characterized in that: Bubbles are uniformly formed between two adjacent layers of the flexible films through intermittent bonding.

5. The fragment recovery device for impact disintegration test according to claim 4, characterized in that: The bubbles are round in shape.

6. The fragment recovery device for impact disintegration test according to claim 5, characterized in that: The distance between two adjacent bubbles is smaller than the diameter of the bubble.

7. The fragment recovery device for impact disintegration test according to claim 5, characterized in that: The diameter of the bubbles is 6 mm to 25 mm; and / or the thickness of the bubbles is 2 mm to 12 mm.

8. The fragment recovery device for impact disintegration test according to any one of claims 3 to 7, characterized in that: The density of the flexible film is 0.015 g / cm 3 -0.045g / cm 3 .

9. The fragment recovery device for impact disintegration test according to any one of claims 3 to 7, characterized in that: The density of the second capture layer is 2-4 times the density of the flexible membrane.

10. The fragment recovery device for impact disintegration test according to any one of claims 1 to 7, characterized in that: The second acquisition layer is a foam board structure.

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